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Sample cases are shown that illustrate the input to the naca456 program for a number of typical airfoils. Only the data between &NACA and / is read by the program. The rest is helpful commentary.

0012

NACA 0012 - four digit airfoil
First two digits indicate no camber
Last two digits indicate max t/c=12 percent
&NACA NAME='NACA 0012', PROFILE='4', TOC=0.12, CAMBER='0'/

[ Examine output for this airfoil. Coarse output.]

6412

NACA 6412 - This airfoil combines a 0012 thickness (four digit) 
with a two-digit 64 camber line. 
A 64 camber line has 6% max camber at 40% chord.
&NACA
 NAME='NACA 6412', dencode=2,
 PROFILE='4', TOC=0.12, 
 CAMBER='2', cmax=0.06, xmaxc=0.4/

[ Examine output for this airfoil. Fine output. ]

16-015

NACA 16-015 - This airfoil is identical to a 0015-45 airfoil.
The modified four-digit thickness has a leading edge index of 4
and the maximum thickness is at 50% chord
&NACA
 NAME='NACA 16-015  [same as 0015-45]'
 profile='4m', leIndex=4, xmaxt=0.5,
 camber='0'/

23012

NACA 23012 - This airfoil combines a 230 mean line (three-digit) 
with a 0012 thickness (four digit). 
A 230 mean line has CL=0.3 and maximum camber at 15% chord.
&NACA
  NAME    = 'NACA 23012', dencode = 3,
  PROFILE = '4', TOC = 0.12,
  CAMBER  = '3',  CL = 0.3,  XCMAX = 0.15/

[ Examine output for this airfoil. Very fine output. ]

63A010

First three characters: 63A series thickness
Fourth character: no camber (CL design=0)
Last two digits: 10 percent t/c
&NACA
 NAME='NACA 63A010', PROFILE='63A', TOC=0.10, CAMBER='0'/

63A409

NACA 63A409
First three characters: 63A series thickness
Fourth character: CL design=0.4
  (63A airfoils always use 6-series modified mean line)
Last two digits: 9 percent t/c
 
&NACA
 NAME='NACA 63A409', 
 PROFILE='63A', TOC=.09, 
 CAMBER='6M', CL=0.4/
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